A gas turbine engine includes a combustor having a combustor air inlet, an axial-centrifugal compressor, a shroud, a secondary flow duct, and a valve. The shroud surrounds at least a portion of the axial-centrifugal compressor and has a surge bleed plenum defined therein that is in fluid communication with, and receives compressed air from, the axial compressor outlet. The secondary airflow duct has a duct inlet that is in fluid communication with the surge bleed plenum, and a duct outlet that is in fluid communication with the combustor air inlet. The valve is mounted on the secondary airflow duct and is movable between a closed position, in which the secondary airflow duct does not provide fluid communication between the surge bleed plenum and the combustor air inlet, and an open position, in which the secondary airflow duct provides fluid communication between the surge bleed plenum and the combustor air inlet.

A liquid cooling head includes an upper casing, an impeller, a bottom casing and a skived fin cooling plate. The upper casing has an inlet and an outlet, the upper casing is fixed on the bottom casing, and the impeller is arranged between the upper casing and the skived fin cooling plate. In addition, the skived fin cooling plate is fixed on the bottom casing, and the impeller sucks the heat-dissipating liquid from the inlet and drives the heat-dissipating liquid passing through the skived fin cooling plate, upwardly passing through the impeller and then discharged from the outlet.

Provided is a radial diffuser that includes a housing, a plurality of diffuser vanes, and a plurality of deswirl vanes and at least one vane extension providing a service routing. Each of the vane extensions is disposed after a radial section and may extend into or through a transition and into the deswirl cascade. At least a portion of the vane extensions include a service passage extending therethrough. Each service passage is configured to allow a service conduit to extend therethrough without adversely crossing either a diffusion flow passage or a transition flow passage.

A heat dissipation fan includes a base plate, a frame formed on a side of the base plate, a stator received sin the frame, and a rotor below the stator and connected with the stator. The heat dissipation fan also has an air inlet, a first air outlet and a second air outlet. The air inlet is communicated with the first air outlet and the second air outlet. An angle is defined between each of the first air outlet and the second air outlet.

A blisk fan is provided for a turbine engine propulsion system. The blisk fan includes a hub configured to rotate about a rotational axis at a maximum rotational speed, and a plurality of blades extending radially outward from the hub to define a fan leading edge tip diameter. Each of the blades has a first vibratory mode at a natural frequency, which is greater than a first fan order and less than a second fan order at the maximum rotational speed. The compression system preferably has a balance factor of the compression system between 1.9 and 3.2.

A system is provided. The system includes a first medium at a first pressure, a second medium at a second pressure, and a medium conditioning sub-system. The medium conditioning sub-system includes a compressor, a first heat exchanger, a second heat exchanger, and a turbine. The turbine receives the first medium and the second medium.

A radial compressor for a compressor arrangement comprising the radial compressor and an axial compressor includes an inlet flow channel bounded by a radially inner hub contour and a radially outer housing contour, in which inlet guide blades are arranged. Via the inlet flow channel a medium to be compressed is supplied to an impeller having moving blades. The inlet flow channel runs diagonally to an axis of rotation of the impeller.

A compressor includes a housing. An impeller is located within the housing and rotatable about an impeller axis in a first rotational direction. A rotor section is rotatable about the impeller axis in a second rotational direction opposite the first rotational direction.

The invention discloses a high-transmission-ratio suspension shaft centrifugal supercharger which comprises a transmission unit, a fan supercharging unit and a cooling unit; the transmission unit is composed of a belt wheel, a planetary gear mechanism, a friction wheel group and a suspension mainshaft, the planetary gear mechanism comprises a sun gear and a planetary gear both installed in a gearbox, the sun gear and the belt wheel are in coaxial installation and rotate together, the planetary gears are distributed at the periphery of the sun gear in a 120 degree symmetric way and are meshed with and follow up the sun gear; the friction wheel group comprises friction wheels arranged in a sealed box and arranged coaxially with corresponding planetary gears; the suspension mainshaft generates contact friction with surfaces of the friction wheels and is driven to rotate together with the friction wheels; the cooling unit is used to pump out high-temperature lubricating oil in the gearbox and the sealed box, and lubricating oil is returned after cooling is performed. According to the invention, the supercharger is substantially improved in transmission precision and speed increasing ratio at a high speed range, and also possesses characteristics of long safe life, convenience for mounting, good heat dispersion performance, low noise and the like.

A compressor includes a housing. An impeller is located within the housing and rotatable about an impeller axis in a first rotational direction. A rotor section is rotatable about the impeller axis in a second rotational direction opposite the first rotational direction.